CN113401348A - Improved deicer aerodynamic integration - Google Patents

Improved deicer aerodynamic integration Download PDF

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Publication number
CN113401348A
CN113401348A CN202110280079.8A CN202110280079A CN113401348A CN 113401348 A CN113401348 A CN 113401348A CN 202110280079 A CN202110280079 A CN 202110280079A CN 113401348 A CN113401348 A CN 113401348A
Authority
CN
China
Prior art keywords
blade
deicer
recess
erosion resistant
leading edge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202110280079.8A
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Chinese (zh)
Inventor
L·普鲁内
A·安杰耶夫斯基
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Latier Fiyac Co ltd
Ratier Figeac SAS
Original Assignee
Latier Fiyac Co ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Latier Fiyac Co ltd filed Critical Latier Fiyac Co ltd
Publication of CN113401348A publication Critical patent/CN113401348A/en
Pending legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/18—Aerodynamic features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/205—Constructional features for protecting blades, e.g. coating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06—Rotors
    • F03D1/065—Rotors characterised by their construction elements
    • F03D1/0675—Rotors characterised by their construction elements of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D80/00—Details, components or accessories not provided for in groups F03D1/00 - F03D17/00
    • F03D80/40—Ice detection; De-icing means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D2045/009—Fire detection or protection; Erosion protection, e.g. from airborne particles
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50—Manufacturing or production processes characterised by the final manufactured product

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Wind Motors (AREA)

Abstract

An improved deicer aerodynamic integration is disclosed herein. The blade deicing system includes: a blade (10) to be deiced having a body (13) extending between a leading edge (11) and a trailing edge (135), the leading edge (11) terminating in an apex (16); the system includes a deicer component (14) having a recess (141) formed therein and positioned on a leading edge (11) of the blade (10) such that the deicer component (14) covers and extends away from the apex (16) and such that the recess (141) is positioned at the apex (16) of the leading edge (11); and an erosion resistant strip (12) provided in the recess (141) of the deicer component (14); wherein the anti-erosion strip (12) and the recess (141) are sized and shaped such that the anti-erosion strip (12) fits within the recess (141) such that an outer surface of the anti-erosion strip is flush with an outer surface of the deicer component (14). A method of manufacturing a blade de-icing system is also described herein.

Description

Improved deicer aerodynamic integration
Technical Field
The present disclosure relates to improvements in de-icers for aircraft blades and methods for manufacturing aircraft blades having these de-icers.
Background
Electrically powered de-icing may be used for aircraft wings or blades. Such electrically powered de-icing may be used, for example, for the leading edge of a helicopter blade or a wind turbine blade. In some systems, the deicing composite may be integrally made with the metal blade to be deiced.
However, improvements in such deicing systems are desirable, and the examples described herein relate to such improvements.
Disclosure of Invention
According to a first aspect, a blade de-icing system is described herein, comprising a blade to be de-iced. The blade has a body extending between a leading edge and a trailing edge, the leading edge terminating in an apex: the system also includes a deicer component having a recess formed therein and positioned on the leading edge of the blade such that the deicer component covers and extends away from the apex and such that the recess is positioned at the apex of the leading edge. Providing an erosion resistant strip in the recess of the deicer component. The erosion resistant strip and the recess are sized and shaped such that the erosion resistant strip fits within the recess such that an outer surface of the erosion resistant strip is flush with an outer surface of the deicer component.
In any of the examples described herein, the erosion resistant strip may be adhesive or self-adhesive, and may be bonded to and within the recess via the adhesive.
In any of the examples described herein, the leading edge may be tapered.
In any of the examples described herein, the body of the blade may also have a recessed section at its leading edge for receiving a deicing component.
In any of the examples described herein, the deicing component may be shaped and sized to fit onto the recessed section of the blade body such that an outer surface of the deicer component is flush with an outer surface of the body.
In any of the examples described herein, the erosion resistant strip may comprise a replaceable strip.
In any of the examples described herein, the deicer component may include a heating element disposed in a matrix. In some examples, the matrix may be an epoxy.
In any of the examples described herein, an erosion resistant coating may be provided to cover at least a portion of an outer surface of the body of the blade.
In any of the examples described herein, a coating may be provided to cover the junction between the deicer component 14 and the body of the blade.
In any of the examples described herein, a coating may be provided to cover the joint between the deicer component and the erosion resistant strip.
Also described herein is a method of manufacturing the above blade de-icing system, the method comprising: providing the blade having a body extending between a leading edge and a trailing edge, the leading edge terminating in an apex; providing a recess in said deicer member and positioning said deicer member on said leading edge of said blade such that said deicer member covers and extends away from said apex and such that said recess is positioned at said apex of said leading edge. The method further includes providing an erosion resistant strip in the recess of the deicer component, wherein the erosion resistant strip and the recess are sized and shaped such that the erosion resistant strip fits within the recess such that an outer surface of the erosion resistant strip is flush with an outer surface of the deicer component.
In some examples, the erosion resistant strip comprises a replaceable self-adhesive strip.
In some examples, the deicer components include heating elements disposed in a matrix, and the matrix may be an epoxy.
In any of the examples described herein, the method may further include providing an erosion resistant coating on the blade such that the coating covers at least a portion of an outer surface of a body of the blade.
In any of the examples described herein, the step of providing the coating may include providing the coating to cover a joint between a deicer component and the blade body.
In any of the examples described herein, the erosion resistant strip may be a replaceable strip.
In any of the examples described herein, the deicer components may include heating elements disposed in a matrix.
In any of the examples described herein, the matrix may include an epoxy resin.
In any of the examples described herein, an erosion resistant coating may be provided to cover at least a portion of an outer surface of the body of the blade.
In any of the examples described herein, a coating may be provided to cover at least a portion of an edge of the deicer component furthest from the apex and the erosion resistant strip.
In any of the examples described herein, a coating may be provided to cover the connection between the edge of the deicer component furthest from the erosion resistant strip and the end of the tapered section of the blade leading edge.
In any of the examples described herein, the method may further include providing an erosion resistant coating on the blade such that the coating covers at least a portion of an outer surface of a body of the blade.
In any of the examples described herein, providing the coating may include providing the coating to cover at least a portion of an edge of the deicer component furthest from the apex and the erosion resistant strip.
In any of the examples described herein, the step of providing the coating may include providing the coating to cover a connection between an edge of the deicer component furthest from the erosion resistant strip and an end of the tapered section of the blade leading edge.
In any of the examples described herein, the blades may be blades of a propeller.
Drawings
Certain embodiments of the present disclosure will now be described in more detail, by way of example only, and with reference to the accompanying drawings, in which:
FIG. 1a shows an exploded view of an example of a prior art blade with a novel deicing system.
FIG. 1b shows the prior art system of FIG. 1a when assembled.
Fig. 2a shows an exploded view of an example of another novel deicing system described herein.
Figure 2b shows the system of figure 2a when assembled.
Detailed Description
The de-icing system described herein includes blades that require de-icing during use, such as blades for helicopters, wind turbines, aircraft, and the like. Examples herein are described with reference to propeller blades.
A novel blade deicing system is described herein and illustrated in FIG. 1. The de-icing system comprises a blade 10 to be de-iced. The blade has a body 3, said body 3 extending from a leading edge 8 to a trailing edge 9. In use, the trailing edge will be attached to a rotor (not shown) of a helicopter. The body 3 may have a section 91, said section 91 having a thickness larger than the section 81 recessed at the leading edge, as shown in fig. 1 a. In some examples, the recess is formed by tapering, and in other examples, the recess is formed by providing a step in the thickness of the body 3 of the blade 10. The deicer elements 4 are positioned in recesses 81 at the front edge 8 and anti-erosion strips 2 may be provided on said deicer elements 4.
A variation of the example shown in fig. 1a and 1b is shown in fig. 2a and 2 b. In this example, the blade has a body 13 extending between a trailing edge 135 and a leading edge 11. In use, the blade will be attached to the rotor of a helicopter or the body of an aircraft or wind turbine by the blade root, which is typically located between the leading edge 11 and the trailing edge 135. The blades may be attached by known techniques. The body 13 of the blade has a main section 133, which main section 133 in the example shown in fig. 1 has a first thickness, which extends to a second section 134 having a second thickness, which is smaller than the first thickness, as shown in fig. 2a, to form a recess in the body 13 of the blade, as in the example shown in fig. 1a and 1 b. Again, this recess may be formed gradually by tapering, or alternatively may be formed by a step of reduced thickness. This second concave section 134 extends in the direction of and to the apex 16 of the blade at its leading edge 11.
A deicer component 14 is provided, said deicer component 14 may be sized and shaped so that it fits closely within this recessed section 134 of reduced thickness of the body 13. The deicer components 14 may be sized and shaped such that when disposed in the recessed section 134, the outer surfaces of the deicer components 14 are flush with the outer surface of the first section 133 of the blade, such that these surfaces are flush with each other and there is no step between their outer surfaces.
The deicer members 14 cover at least a portion of the leading edge 11 of the blade as shown in fig. 2a and 2 b. The deicer assembly 14 may also extend to cover the upper and lower surfaces of the blade in use.
In some examples, deicer assembly 14 may include one or more heating elements embedded in a resin or other matrix that provides erosion protection and also insulates the heating elements. In some examples, the heating element may comprise a metal foil strip that is resistive and generates heat by joule effect when connected to a power source. Other heating elements and substrates are also contemplated.
As shown in fig. 2a and 2b, erosion resistant strips 12 are also provided to be positioned at the apex 16 of the leading edge or at the apex 16 and on top of the deicing member 14. In the example shown in fig. 2a and 2b, the deicer component 14 can be shaped such that it has a region of reduced thickness at the apex 16 to form a recess 141 in the deicer component for receiving the erosion resistant bar 12.
The size and shape of the recess 141 of the deicing member 14 may be designed and the size and shape of the erosion resistant bar 12 may also be designed such that the erosion resistant bar 12 fits tightly in the recess 141 such that the outer surface of the erosion resistant bar 12 is flush with the outer surface of the deicing member 14 when the erosion resistant bar 12 is in place, such that there is no step in the height of the outer surface.
In some examples, the erosion resistant strip 12 is a replaceable strip. In some examples, the erosion resistant strip 12 may include a polyurethane film. This strip 12 is adhesive and in some examples, the strip may be self-adhesive. In other examples, the strip may require the addition of an adhesive. Such adhesive strips can be easily debonded and replaced with new adhesive strips if necessary. The 3M company is the supplier of such corrosion resistant strips. In other examples, the strip may be a thermoplastic film with an adhesive added. Any other material that provides good erosion resistance may also or alternatively be used.
In some examples, the body of the blade may also have a layer of paint (not shown) provided on the outer surface of the body 13 of the blade 10. The coating may comprise an erosion resistant coating. In some examples, this coating may be sprayed onto the body of the blade after the blade has been completed or equipped. Such an erosion resistant coating may provide erosion protection to the remainder of the propeller blade. In some examples, the coating may be applied to the blade such that the coating covers at least a portion or edge of the deicer member 14, thereby providing a smooth transition between the interface including the edge of the deicer member 14 disposed in the recess of the blade and the outer surface of the blade adjacent to the recess.
A method of manufacturing such a blade 10 with a deicing system may include providing such a blade 10 by known techniques such that the blade 10 has the above-described characteristics, i.e., the body 13 extending to the apex 16 of the tapered leading edge 11. The method may further include providing a deicing member 14 as described above, wherein the deicing member 14 has a concave section 141, and bonding the deicing member 14 to the blade 10 such that the concave section 141 of the deicing member is positioned at the apex 16 of the leading edge 11 of the blade. In examples where the deicing member 14 is provided to be positioned in a recess of a blade, the method may further comprise first forming this recess in the blade by tapering the thickness or providing a step change in the blade thickness.
The method may further include providing the erosion resistant strip 12 such that it is positioned to fit closely within the recessed section 141 of the deicing component 14 such that the outer surface of the erosion resistant strip 12 is flush with the outer surface of the deicing component 14, as shown in fig. 2 b.
The erosion resistant strip may be adhesive and the step of providing such strip may comprise adhering the strip 12 to the deicing member 14, and more particularly, adhering the strip 12 to the recessed section 141 of the deicing member 14 such that the strip is positioned at the apex of the blade 10 in use such that there is no step between the erosion resistant strip 12 and the deicing member 14. In some examples, the method may further include providing a coating on an outer surface of the body 13 of the blade 10 as described above.
Thus, in this method, the deicer components 14 are formed such that they bond to the tapered leading edge of the blade 10, and the erosion resistant bar 12 is in turn also bonded to the deicer components 14. The erosion resistant strip 12 may be a polyurethane or elastomeric strip and may be self-adhesive.
The systems and methods described herein provide advantages over known deicing systems and methods because the blades also have improved aerodynamic properties.
In addition to this, since the erosion resistant device is integrated with the deicer assembly 14 by adhesive bonding, the combination of the erosion resistant strip 12 and deicer assembly 14 forms a smooth outer surface/shape on the outer surface of the blade after the strip 12 has been bonded to the deicer. This improves the aerodynamic properties of the blade/propeller compared to the case where there is a step between the erosion resistant strip 12 and the deicer segments 14. If there is a step between these two parts, aerodynamic turbulence will be generated, which in the case of a propeller will reduce its efficiency.

Claims (14)

1. A blade de-icing system comprising
The blade (10) having a body (13) extending between a leading edge (11) and a trailing edge (135), the leading edge (11) terminating in an apex (16);
the system includes a deicer component (14) having a recess (141) formed therein and positioned on the leading edge (11) of the blade (10) such that the deicer component (14) covers and extends away from the apex (16) and such that the recess (141) is positioned at the apex (16) of the leading edge (11);
and
an erosion resistant strip (12) disposed in the recess (141) of the deicer component (14);
wherein the erosion resistant strip (12) and the recess (141) are sized and shaped such that the erosion resistant strip (12) fits within the recess (141) such that an outer surface of the erosion resistant strip is flush with an outer surface of the deicer component (14).
2. The system of claim 1, wherein the erosion resistant strip (12) is adhesive and bonded to the recess (141) via the adhesive.
3. A system according to claim 1 or 2, wherein the leading edge (11) is tapered.
4. The system of any preceding claim, wherein at the leading edge (11), the body of the blade has a recessed section (134).
5. The system of claim 4, wherein the deicer component (14) is shaped and sized to fit onto the recessed section (134) of the blade body (13) such that the outer surface of the deicer component (14) is flush with the outer surface of the body (13).
6. The system of any preceding claim, wherein the erosion resistant strip (12) comprises a replaceable strip.
7. The system of any preceding claim, wherein the deicer component (14) comprises a heating element disposed in a matrix.
8. The system of claim 7, wherein the matrix is an epoxy.
9. The system of any preceding claim, wherein an erosion resistant coating is provided to cover at least a portion of the outer surface of the body (13) of the blade (10).
10. The system of claim 9, wherein the coating is provided to cover a junction between the deicer component 14 and the body (13) of the blade (10).
11. The system of claim 8 or 9, wherein the coating is provided to cover a joint between the deicer component (14) and erosion resistant strip (12).
12. A method of manufacturing a blade de-icing system comprising
Providing the blade (10) with a body (13) extending between a leading edge (11) and a trailing edge (135), the leading edge (11) terminating in an apex (16);
providing a recess (141) in the deicer member (14) and positioning the deicer member (14) on the leading edge (11) of the blade (10) such that the deicer member (14) covers and extends away from the apex (16) and such that the recess (141) is positioned at the apex (16) of the leading edge (11);
and
-providing an erosion resistant strip (12) in the recess (141) of the deicer member (14);
wherein the erosion resistant strip (12) and the recess (141) are sized and shaped such that the erosion resistant strip (12) fits within the recess (141) such that an outer surface of the erosion resistant strip is flush with an outer surface of the deicer component (14).
13. The method of claim 12, further comprising providing an erosion resistant coating on the blade such that the coating covers at least a portion of the outer surface of the body (13) of the blade (10).
14. The method according to claim 12 or 13, wherein the step of providing the coating comprises providing the coating to cover the joint between a deicer member (14) and the blade body (13).
CN202110280079.8A 2020-03-16 2021-03-16 Improved deicer aerodynamic integration Pending CN113401348A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP20305270.9 2020-03-16
EP20305270.9A EP3882131A1 (en) 2020-03-16 2020-03-16 Improvement deicer aerodynamic integration

Publications (1)

Publication Number Publication Date
CN113401348A true CN113401348A (en) 2021-09-17

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US (1) US20210284345A1 (en)
EP (1) EP3882131A1 (en)
CN (1) CN113401348A (en)
BR (1) BR102021000585A2 (en)
CA (1) CA3108983A1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4389597A1 (en) * 2022-12-21 2024-06-26 Airbus Operations GmbH Aircraft structure component for laminar flow

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GB662110A (en) * 1949-07-11 1951-11-28 Dehavilland Aircraft Improvements in aircraft propeller and rotor blades
US2464273A (en) * 1947-03-12 1949-03-15 Tanchel Melvin Decing device for airfoils
US2992317A (en) * 1957-10-14 1961-07-11 Goodrich Co B F Electrically heated ice-removal apparatus
US5449134A (en) * 1993-09-24 1995-09-12 The B. F. Goodrich Company Apparatus and method for providing a pneumatic de-icer with a replaceable environment resistant surface
US5558304A (en) * 1994-03-14 1996-09-24 The B. F. Goodrich Company Deicer assembly utilizing shaped memory metals
EP0872417A1 (en) * 1997-04-16 1998-10-21 The B.F. Goodrich Company Hybrid deicer
FR2866000B1 (en) * 2004-02-11 2007-04-06 Eurocopter France HEATING MATERIAL COMPOSED OF ELECTRICALLY CONDUCTIVE FIBERS.
ES2693679T3 (en) * 2012-10-31 2018-12-13 Saab Ab A porous coating applied to an air article
EP4120796A3 (en) * 2015-01-06 2023-05-03 Battelle Memorial Institute Uniform heat distribution in resistive heaters for anti-icing and de-icing
US10533533B2 (en) * 2015-08-26 2020-01-14 General Electric Company Modular wind turbine rotor blade constructed of multiple resin systems
US10648456B2 (en) * 2016-10-21 2020-05-12 General Electric Company Organic conductive elements for deicing and lightning protection of a wind turbine rotor blade
US11542920B2 (en) * 2017-05-30 2023-01-03 Siemens Gamesa Renewable Energy A/S Insulation of a heating mat of a wind turbine blade
EP3560822A1 (en) * 2018-04-26 2019-10-30 3M Innovative Properties Company Anti-icing stack
WO2021007797A1 (en) * 2019-07-17 2021-01-21 3M Innovative Properties Company Thin electrothermal film heater with variable thermal output

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US20210284345A1 (en) 2021-09-16
BR102021000585A2 (en) 2021-09-28
EP3882131A1 (en) 2021-09-22
CA3108983A1 (en) 2021-09-16

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